Effect of Exit-Slot Position and Opening on the Available Cooling Pressure for N.A.C.A. Nose-Slot Cowlings

Abstract

Full-scale nose-slot cowlings were tested in a wind tunnel to furnish information on the pressure drop available for cooling. Of the two basic nose shapes tested, the one with the smaller radius of curvature gave the higher pressure drop across the engine. The maximum pressure drop for high-speed conditions with an engine conductance equivalent to a double-row radial engine is 1.45 and for take-off conditions it is 3.75. When using a propeller with a round blade shank, the values are 1.23 and 1.65 respectively.

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Document Details

Document Type
Technical Report
Publication Date
Jan 18, 1939
Accession Number
ADB806614

Entities

People

  • George W. Stickle
  • Irven Naiman
  • John L. Crigler

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Aeronautics
  • Blades
  • Coefficients
  • Curvature
  • Dynamic Pressure
  • Efficiency
  • Flight
  • Flow
  • High Pressure
  • Measurement
  • Pressure Distribution
  • Propeller Blades
  • Propellers
  • Shape
  • Static Pressure
  • Wind Tunnels

Readers

  • Aerodynamics/Aeronautics.
  • Internal Combustion Engine (ICE) Technology.
  • Structural Health Monitoring of Composite Structures.